CN112503572B - Combustion chamber with oscillation combustion detection and inhibition functions - Google Patents
Combustion chamber with oscillation combustion detection and inhibition functions Download PDFInfo
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- CN112503572B CN112503572B CN202011387085.5A CN202011387085A CN112503572B CN 112503572 B CN112503572 B CN 112503572B CN 202011387085 A CN202011387085 A CN 202011387085A CN 112503572 B CN112503572 B CN 112503572B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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Abstract
The application belongs to the technical field of gas turbine combustor design, in particular to combustor with oscillating combustion detects and inhibit function includes: a flame tube; a value class fuel nozzle which is arranged at the center of the circular end surface of the head of the flame tube; the main-stage fuel nozzles are uniformly arranged on the circular end surface in a surrounding way; the plurality of fuel adjusting nozzles are arranged on the flame tube cylinder body in a penetrating way and are divided into at least one group; the total pressure test probe is arranged on each adjusting fuel nozzle and used for monitoring the pressure of the inner cavity of the flame tube at the position of the total pressure test probe in real time; and the logic controller is used for receiving the pressure data and controlling the adjusting fuel nozzle at the corresponding position of the measuring point. The combustion chamber with the oscillatory combustion detection and suppression function can monitor the pressure change in the combustion chamber in the whole process, and can distinguish whether oscillatory combustion occurs in the combustion chamber or not at the first time; in addition, after the oscillation combustion occurs in the combustion chamber, the oil-gas ratio can be increased through local oil injection, and the oscillation combustion can be restrained and eliminated.
Description
Technical Field
The application belongs to the technical field of gas turbine combustor design, and particularly relates to a combustor with oscillating combustion detection and suppression functions.
Background
In the design of civil aircraft and gas turbine combustion chambers, the emission index is strictly required, so a lean premixed combustion organization technology is mostly adopted, and the use of the technology is easy to cause unstable combustion so as to further cause oscillatory combustion; the oscillatory combustion is a self-oscillation phenomenon mainly generated by mutual interaction and coupling between the pulsation of flame heat release and a sound field in a combustion chamber during combustion. When the combustion chamber takes place the oscillation combustion, powerful pressure pulsation can lead to the combustion chamber and even whole engine vibration aggravation, sends huge combustion noise, influences the performance of engine, makes engine parts suffer destruction and burning when serious, also aggravates the production of pollutant simultaneously. Therefore, rapid identification and control of the problem of the oscillatory combustion is very important.
The prior art solution controls the problem of the oscillatory combustion mainly by adjusting the aerodynamic layout of the combustion chamber. For example, baffles are added or the structure of the swirler is improved, and the backflow strength is enhanced to improve the combustion stability.
The main disadvantages of the existing solutions are as follows:
1. the existing control method cannot monitor the pressure change in the combustion chamber and cannot judge whether the oscillatory combustion occurs.
2. The existing control method is a passive control method, and can only reduce the probability of oscillation combustion, such as the oscillation combustion in the working process of a combustion chamber without oscillation combustion inhibition measures.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present application provides a combustion chamber with an oscillating combustion detection and suppression function.
The application discloses combustion chamber with oscillating combustion detects and inhibit function includes:
the inner cavity at the head of the flame tube is a premixing cavity, and a mixing hole is formed in the flame tube at the backward position of the outlet of the premixing cavity;
the value class fuel nozzle is arranged at the center of the circular end face of the head of the flame tube and used for starting ignition of a combustion chamber and working in a small state;
the main-stage fuel nozzles are uniformly arranged on the circular end surface in a surrounding manner by taking the center of the circular end surface of the head of the flame tube as a circle center and are used for working in a large state of a combustion chamber;
the adjusting fuel nozzles penetrate through the barrel body between the end face of the head of the flame tube and the mixing hole, the adjusting fuel nozzles are divided into at least one group, and each group is uniformly distributed on the barrel body in an annular shape;
the total pressure test probe is arranged on each adjusting fuel nozzle, extends into the inner cavity of the flame tube along with the adjusting fuel nozzle and is used for monitoring the pressure of the inner cavity of the flame tube at the position of the adjusting fuel nozzle in real time;
and the logic controller is used for receiving the pressure data monitored by the total pressure test probe and judging whether oscillatory combustion can be caused or not according to the pressure data so as to control the opening of the fuel nozzle at the corresponding position of the test point when the oscillatory combustion can be caused.
According to at least one embodiment of the application, a plurality of adjusting fuel nozzles are distributed on the flame tube cylinder body in three groups, the number of the adjusting fuel nozzles in each group is the same as that of the adjusting fuel nozzles in the primary stage, and in addition, the adjusting fuel nozzles in the three groups are distributed at equal intervals in the axial direction of the flame tube.
In accordance with at least one embodiment of the subject application, the three sets of tuning fuel injectors, the first set of tuning fuel injectors being first tuning fuel injectors, the second set of tuning fuel injectors being second tuning fuel injectors, and the third set of tuning fuel injectors being third tuning fuel injectors;
the first group of a plurality of first adjusting fuel nozzles are located at the axial middle position of the flame tube premixing cavity, the second group of a plurality of second adjusting fuel nozzles are located at the outlet position of the flame tube premixing cavity, and the third group of a plurality of third adjusting fuel nozzles are located at the front section position of the mixing hole.
According to at least one embodiment of the present application, the plurality of first rings at the axial midpoint of the premix barrel adjust the mounting locations of the fuel nozzles in one-to-one correspondence with the locations of the plurality of primary stage fuel nozzles;
according to the rotation direction of the swirler, the second adjusting fuel nozzles at the outlet position of the premixing cavity rotate 30 degrees clockwise relative to the first adjusting fuel nozzles at the axial midpoint of the premixing cavity;
and according to the rotation direction of the swirler, the third adjusting fuel nozzles at the front sections of the mixing holes rotate 60 degrees clockwise relative to the first adjusting fuel nozzles at the axial middle points of the premixing cavities.
According to at least one embodiment of the present application, the logic controller is configured to:
if the pressure signal monitored by one or more monitoring points is abnormal, continuously monitoring an abnormal pressure pulsation signal for 10s, and if the pulsation is reduced and the pressure signal is recovered to be normal, the pressure signal is normal pulsation and cannot cause oscillation combustion;
and if the abnormal pressure pulsation signal still exists after 10s and has an increasing trend, opening the adjusting fuel nozzle at the corresponding position of the measuring point.
According to at least one embodiment of the application, the number of the main-stage fuel nozzles is six, and the main-stage fuel nozzles are uniformly arranged on the circular end face in a surrounding mode.
The application has at least the following beneficial technical effects:
the combustion chamber with the oscillatory combustion detection and suppression function can monitor the pressure change in the combustion chamber in the whole process, and can distinguish whether oscillatory combustion occurs in the combustion chamber or not at the first time; in addition, after the oscillation combustion occurs in the combustion chamber, the fuel-air ratio can be increased through local fuel injection, and the oscillation combustion can be restrained and eliminated.
Drawings
FIG. 1 is a perspective view of a combustion chamber with oscillating combustion detection and suppression of the present application;
FIG. 2 is a cross-sectional view of a combustion chamber with the oscillatory combustion detection and suppression of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
It should be understood that technical terms such as "central", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., which may be referred to in the description of the present application, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the scope of the present application.
The principle of this application is based on the heat release inequality that the oscillatory combustion mainly caused by fuel unstable combustion with the sound field coupling in the combustion chamber with cause, take place the oscillatory combustion and can lead to the fact the destruction to the structure of combustion chamber, the oscillatory combustion concrete performance is the pressure surge in the combustion chamber in the work, this application adopts the method of monitoring the interior gas pressure of flame tube often, judge whether the oscillatory combustion takes place, at first according to combustion chamber overall structure form, arrange pressure monitoring point at flame tube typical position, monitor pressure variation often, judge whether the oscillatory combustion takes place. When pressure is abnormal, oscillation combustion occurs at a high probability, the oil-gas ratio of the position is increased according to the rule that the oscillation combustion occurrence probability is approximately inversely proportional to the local oil-gas ratio, combustion stability is improved, and the oscillation combustion phenomenon is restrained and eliminated at the first time.
The combustion chamber with the oscillatory combustion detection and suppression of the present application will be described in further detail with reference to fig. 1-2.
The application discloses combustion chamber with oscillating burning detects and suppresses function, as shown in fig. 1, this combustion chamber mainly contains value class fuel nozzle 1, main grade fuel nozzle 2, first regulation fuel nozzle 3, second regulation fuel nozzle 4, third regulation fuel nozzle 5 and flame tube 6.
The inner cavity at the head position (left side in fig. 1) of the flame tube 6 is a premixing cavity, and the flame tube 6 at the backward position of the outlet of the premixing cavity is provided with a mixing hole 61.
A value class fuel nozzle 1 is arranged at the center of the circular end face of the head of the flame tube 6 and used for starting ignition of a combustion chamber and working in a small state.
The main-stage fuel nozzles 2 are uniformly arranged on the circular end face in a surrounding mode by taking the center of the circular end face at the head of the flame tube 6 as a circle center and are used for working in a large state of a combustion chamber.
A plurality of fuel nozzles of adjusting run through the setting on the barrel between 6 head terminal surfaces of flame tube to mixing hole 61, a plurality of fuel nozzles of adjusting divide into at least one group, and every group is cyclic annular evenly distributed on the barrel.
The total pressure test probe 7 is arranged on each adjusting fuel nozzle, extends into the inner cavity of the flame tube 6 along with the adjusting fuel nozzle, and is used for monitoring the pressure of the inner cavity of the flame tube 6 at the position of the total pressure test probe in real time.
The logic controller is used for receiving pressure data monitored by the total pressure test probe 7, judging whether oscillatory combustion can be caused or not according to the pressure data, and controlling the opening of the adjusting fuel nozzle at the corresponding position of the test point when the oscillatory combustion can be caused.
Further, the number of the main-stage fuel injectors 2 and the number of the pilot fuel injectors may be appropriately selected as needed, and in the present embodiment, six main-stage fuel injectors 2 are arranged on each combustor basket 6.
The plurality of adjusting fuel nozzles are distributed in three groups on the cylinder body of the flame tube 6, the number of each group of adjusting fuel nozzles is the same as that of the main-stage fuel nozzles 2 (namely, the number of each group of adjusting fuel nozzles is six in the embodiment), and in addition, the three groups of adjusting fuel nozzles are distributed at equal intervals in the axial direction of the flame tube 6.
Further, referring to fig. 1 and 2, the three groups of adjusting fuel nozzles include a first group of adjusting fuel nozzles 3, a second group of adjusting fuel nozzles 4 and a third group of adjusting fuel nozzles 5. The six first adjusting fuel nozzles 3 of the first group are located at the axial middle point of a premixing cavity of the flame tube 6, the six second adjusting fuel nozzles 4 of the second group are located at the outlet of the premixing cavity of the flame tube 6, and the six third adjusting fuel nozzles 5 of the third group are located at the front section of the mixing hole 61. Note that no fuel burns after the dilution holes 61, and therefore no fuel nozzle is provided for adjustment.
Further, the flame tube 6 is a place for burning fuel, the pressure change in the main combustion area is the most severe, and the first adjusting fuel nozzles 3 mainly monitor the pressure change in the main combustion area, so that the installation positions of the six first adjusting fuel nozzles 3 at the axial middle point of the premixing cavity preferably correspond to the positions of the six main-stage fuel nozzles 2 one by one.
In addition, because the air flow deflects along with the rotation direction of the swirler in the flowing process of the air flow in the combustion chamber, according to the rotation direction of the swirler, six second adjusting fuel nozzles 4 at the outlet position of the premixing cavity rotate 30 degrees clockwise relative to six first adjusting fuel nozzles 3 at the axial midpoint of the premixing cavity; and the six third adjusted fuel injectors 5 at the front section of the dilution hole are rotated 60 clockwise relative to the six first adjusted fuel injectors 3 at the axial midpoint of the premix barrel.
In actual work, the pressure change conditions of 18 measuring points are monitored at any time, and pressure pulsation data are transmitted to a logic controller; the logic controller is configured to continuously monitor an abnormal pressure pulsation signal 10s if a certain monitoring point or a plurality of monitoring points monitor abnormal signals, and if the pulsation is reduced and the signals are recovered to be normal, the signals are normal pulsation and do not cause oscillatory combustion; if the abnormal pressure pulsation signal still exists and tends to increase after 10s, the adjusting fuel nozzle at the corresponding position of the measuring point is opened, the fuel-air ratio of the area near the measuring point is increased through fuel injection, the fuel-air combustion stability is improved after the fuel-air ratio is increased, the oscillation combustion is restrained and finally eliminated.
In summary, the combustion chamber with the oscillatory combustion detection and suppression function can monitor the pressure change in the combustion chamber in the whole process, and can distinguish whether oscillatory combustion occurs in the combustion chamber at the first time; in addition, after the oscillation combustion occurs in the combustion chamber, the oil-gas ratio can be increased through local oil injection, and the oscillation combustion can be restrained and eliminated.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (2)
1. A combustion chamber with oscillating combustion detection and suppression, comprising:
the inner cavity of the head of the flame tube (6) is a premixing cavity, and a mixing hole (61) is formed in the flame tube (6) at the backward position of the outlet of the premixing cavity;
a value class fuel nozzle (1) which is arranged at the center of the circular end face of the head of the flame tube (6) and is used for starting ignition of a combustion chamber and working in a small state;
the main-stage fuel nozzles (2) are uniformly arranged on the circular end surface in a surrounding manner by taking the center of the circular end surface at the head of the flame tube (6) as a circle center, and are used for working in a large state of a combustion chamber;
the plurality of adjusting fuel nozzles penetrate through the barrel body between the end face of the head of the flame tube (6) and the mixing hole (61), the plurality of adjusting fuel nozzles are divided into at least one group, and each group is uniformly distributed on the barrel body in an annular shape;
the total pressure test probe (7) is arranged on each adjusting fuel nozzle, extends into the inner cavity of the flame tube (6) along with the adjusting fuel nozzle and is used for monitoring the pressure of the inner cavity of the flame tube (6) at the position of the total pressure test probe in real time;
the logic controller is used for receiving pressure data monitored by the total pressure test probe (7), judging whether oscillatory combustion can be caused or not according to the pressure data, and controlling the opening of a regulating fuel nozzle at a corresponding position of a test point when the oscillatory combustion can be caused;
the plurality of adjusting fuel nozzles are distributed on the flame tube (6) body into three groups, the number of each group of adjusting fuel nozzles is the same as that of the main-stage fuel nozzles (2), and in addition, the three groups of adjusting fuel nozzles are distributed at equal intervals in the axial direction of the flame tube (6);
in the three groups of adjusting fuel nozzles, the first group of adjusting fuel nozzles is a first adjusting fuel nozzle (3), the second group of adjusting fuel nozzles is a second adjusting fuel nozzle (4), and the third group of adjusting fuel nozzles is a third adjusting fuel nozzle (5);
the first group of a plurality of first adjusting fuel nozzles (3) are positioned at the axial middle point of a premixing cavity of the flame tube (6), the second group of a plurality of second adjusting fuel nozzles (4) are positioned at the outlet position of the premixing cavity of the flame tube (6), and the third group of a plurality of third adjusting fuel nozzles (5) are positioned at the front section of the mixing hole (61);
the mounting positions of the first adjusting fuel nozzles (3) at the axial midpoint of the premixing cavity correspond to the positions of the main-stage fuel nozzles (2) one by one;
according to the rotation direction of the swirler, a plurality of second adjusting fuel nozzles (4) at the outlet position of the premixing cavity rotate 30 degrees clockwise relative to a plurality of first adjusting fuel nozzles (3) at the axial midpoint of the premixing cavity;
according to the rotation direction of the swirler, a plurality of third adjusting fuel nozzles (5) at the front section of the mixing hole rotate 60 degrees clockwise relative to a plurality of first adjusting fuel nozzles (3) at the axial midpoint of the premixing cavity;
the logic controller is configured to:
if the pressure signal monitored by one or more monitoring points is abnormal, continuously monitoring an abnormal pressure pulsation signal for 10s, and if the pulsation is reduced and the pressure signal is recovered to be normal, the pressure signal is normal pulsation and oscillation combustion cannot be caused;
and if the abnormal pressure pulsation signal still exists after 10s and has an increasing trend, opening the adjusting fuel nozzle at the corresponding position of the measuring point.
2. The combustion chamber with the oscillating combustion detecting and suppressing function as claimed in claim 1, wherein the number of the main stage fuel injection nozzles (2) is six and is uniformly arranged around a circular end surface.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011387085.5A CN112503572B (en) | 2020-12-01 | 2020-12-01 | Combustion chamber with oscillation combustion detection and inhibition functions |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011387085.5A CN112503572B (en) | 2020-12-01 | 2020-12-01 | Combustion chamber with oscillation combustion detection and inhibition functions |
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| CN112503572A CN112503572A (en) | 2021-03-16 |
| CN112503572B true CN112503572B (en) | 2022-10-28 |
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| CN115218220B (en) * | 2022-09-01 | 2023-01-17 | 中国航发四川燃气涡轮研究院 | Hot spot migration control design method for main combustion chamber |
| CN116293815A (en) * | 2023-03-22 | 2023-06-23 | 无锡明阳氢燃动力科技有限公司 | Low nitrogen hydrogen combustion chamber structure |
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| US6058709A (en) * | 1996-11-06 | 2000-05-09 | The United States Of America Represented By The United States Department Of Energy | Dynamically balanced fuel nozzle and method of operation |
| CN203757766U (en) * | 2013-12-10 | 2014-08-06 | 中国燃气涡轮研究院 | Rich oil direct-mixing partitioning combustion chamber |
| CN105971737B (en) * | 2016-05-09 | 2017-08-29 | 西北工业大学 | A kind of sequential control method for improving punching engine ignition success rate |
| EP3369995B1 (en) * | 2017-03-02 | 2020-08-05 | Ansaldo Energia Switzerland AG | Method of flow oscillation cancellation in a mixer |
| CN107062307B (en) * | 2017-05-09 | 2023-06-20 | 新奥能源动力科技（上海）有限公司 | Combustion chamber of gas turbine |
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